CN109606612A - Extraordinary unmanned plane structure-function integration bay section and extraordinary unmanned plane - Google Patents
Extraordinary unmanned plane structure-function integration bay section and extraordinary unmanned plane Download PDFInfo
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- CN109606612A CN109606612A CN201811618423.4A CN201811618423A CN109606612A CN 109606612 A CN109606612 A CN 109606612A CN 201811618423 A CN201811618423 A CN 201811618423A CN 109606612 A CN109606612 A CN 109606612A
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- 230000010354 integration Effects 0.000 title claims abstract description 32
- 239000007788 liquid Substances 0.000 claims abstract description 110
- 238000001816 cooling Methods 0.000 claims abstract description 69
- 239000002826 coolant Substances 0.000 claims abstract description 46
- 238000012423 maintenance Methods 0.000 claims abstract description 19
- 230000003014 reinforcing effect Effects 0.000 claims abstract description 10
- 230000002708 enhancing effect Effects 0.000 claims abstract description 3
- 239000002131 composite material Substances 0.000 claims description 18
- 238000009434 installation Methods 0.000 claims description 13
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 11
- 229910052799 carbon Inorganic materials 0.000 claims description 11
- 229910000838 Al alloy Inorganic materials 0.000 claims description 7
- 239000004593 Epoxy Substances 0.000 claims description 7
- 239000000835 fiber Substances 0.000 claims description 6
- 239000000463 material Substances 0.000 claims description 5
- 229920000784 Nomex Polymers 0.000 claims description 4
- 239000004763 nomex Substances 0.000 claims description 4
- 239000000110 cooling liquid Substances 0.000 claims description 3
- 239000002657 fibrous material Substances 0.000 claims description 2
- 238000012360 testing method Methods 0.000 claims description 2
- 238000009423 ventilation Methods 0.000 claims description 2
- 238000000034 method Methods 0.000 abstract description 5
- 238000013461 design Methods 0.000 description 23
- 230000006870 function Effects 0.000 description 11
- 238000010586 diagram Methods 0.000 description 7
- 238000012857 repacking Methods 0.000 description 5
- 230000008901 benefit Effects 0.000 description 4
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- 230000001413 cellular effect Effects 0.000 description 2
- 238000001514 detection method Methods 0.000 description 2
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/068—Fuselage sections
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
- B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
- B64D13/08—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned the air being heated or cooled
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D9/00—Equipment for handling freight; Equipment for facilitating passenger embarkation or the like
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Health & Medical Sciences (AREA)
- General Health & Medical Sciences (AREA)
- Pulmonology (AREA)
- Cooling Or The Like Of Electrical Apparatus (AREA)
Abstract
The invention discloses a kind of extraordinary unmanned plane structure-function integration bay section and extraordinary unmanned planes, the described method includes: cargo tank structure body, for passing through payload module loading area installed load module, and liquid cooling cycle cooling system is installed, by the reinforcing frame being set between payload module loading area, enhancing structure intensity and the aerodynamic configuration for maintaining integrated bay section exterior skin；Payload module, for undertaking mission payload；Cable and connector, for realizing the connection of the payload module and external tasks electronic equipment；Liquid cooling cycle cooling system, comprising: coolant duct, heat carrier, liquid supply assembly, gas-liquid heat exchanger and its air passage；Safeguard that hatch door, including top maintenance hatch door, two sides maintenance hatch door and bottom safeguard hatch door.
Description
Technical field
The present invention relates to extraordinary air vehicle technique field more particularly to a kind of extraordinary unmanned plane structure-function integration bay sections
With extraordinary unmanned plane.
Background technique
The basic development mode of extraordinary unmanned plane is on the close medium-and-large-sized unmanned aerial vehicle platform of existing performance characterisitic
Execute the airborne electronic equipment of particular task adds repacking design and integrated verification, such as early warning detection, scouting, fight, refer to
It the system-wide repacking design of the integrated extraordinary unmanned plane of multi-sensor devices such as waves, control and verifying, as shown in Figure 1.
Currently, having developed mature unmanned aerial vehicle platform according to the basic of extraordinary unmanned plane plus repacking development mode, the country
Maximum carries weight/center of gravity limitation, arrangement space constraint, and the resources such as maximum power supply and distribution and heat-sinking capability are still able to satisfy below deck equipment
The installation demand of the few single task role load system low with heat consumption of quantity.But it is more seriously to restrict below deck equipment quantity, heat
Consume the integrated of big multitask load system.Wherein, inner electronic equipment basic installation mode in extraordinary unmanned aerial vehicle platform cabin causes
Bearing structure multiplexing ratio is lower, and weight is big, and space utilization rate is not high in cabin, and layout is nervous.Meanwhile extraordinary unmanned plane is flat
Platform, for example the task electronic system power consumption of unmanned early warning detection is up to 30Kw or with higher, the medium-and-large-sized nothing of domestic existing development
Man-machine platform all lacks the closed cycle heat control system worked normally suitable for high power electronic equipment.
Summary of the invention
The embodiment of the present invention provides a kind of extraordinary unmanned plane structure-function integration bay section and extraordinary unmanned plane, to solve
The above problem in the prior art.
The embodiment of the present invention provides a kind of extraordinary unmanned plane structure-function integration bay section, comprising:
Cargo tank structure body for passing through payload module loading area installed load module, and installs liquid cooling cycle cooling system,
By the reinforcing frame being set between payload module loading area, enhancing structure intensity simultaneously maintains the pneumatic of integrated bay section exterior skin
Shape；
Payload module is installed in the payload module loading area of the cargo tank structure body, for undertaking mission payload；
Cable and connector are connect with the payload module, are set for realizing the payload module and external tasks electronics
Standby connection；
Liquid cooling cycle cooling system, comprising: coolant duct, heat carrier, liquid supply assembly, gas-liquid heat exchanger and its ventilation
Road, wherein liquid supply assembly, gas-liquid heat exchanger and its air passage are mounted on the integrated cabin segment trailer and the cargo tank structure
Body and the side opposite with flight course, coolant duct and heat carrier are integrated in cargo tank structure body, for the bay section
Structural body radiates；
Safeguard that hatch door, including top maintenance hatch door, two sides maintenance hatch door and bottom safeguard hatch door, wherein the top
Maintenance hatch door is set to the top of cargo tank structure body, and the two sides maintenance hatch door is set to the two sides of the cargo tank structure body, institute
The bottom that bottom maintenance hatch door is set to the cargo tank structure body is stated, for facilitating payload module, cable and connector and liquid
The handling replacement of SAPMAC method cooling system and daily maintenance.
Preferably, the cargo tank structure body specifically includes: multiple payload module loading areas, and each payload module loading area is logical
It crosses heat carrier to separate, front-back installs aluminium alloy base plate inside each payload module loading area, and backboard, top installation are installed in bottom
It is electromagnetically shielded seal cover board, is used for installed load module inside the payload module loading area, and be provided with built-in fitting and installation
Hole keeps the telecommunication functor of original machine case；The interface of the bottom pre- testing cable and connector of the payload module loading area；It is carrying
Reinforcing frame is provided between lotus module loading area.
Preferably, the cargo tank structure body is manufactured for integration, and reinforcing frame assembling is spliced；The cargo tank structure
Body is molecular multiple using T700 carbon/epoxy composite material panel and T700 carbon/epoxy composite material panel and Nomex honeycomb core
Close sandwich.
Preferably, the liquid cooling cycle cooling system specifically includes: coolant duct, heat carrier, liquid supply assembly, gas-liquid heat
Exchanger and its air passage, wherein the liquid supply assembly is by pump, liquid reserve tank, control valve and filter is integrated forms,
For providing driving force to coolant liquid, overcomes flow resistance, be input to coolant duct liquid inlet；The heat carrier is set to two
Between the aluminium alloy base plate of a payload module loading area and the head-tail of payload module loading area, for exporting the payload module
The heat generated when work is into the coolant liquid of coolant duct；The coolant duct is set in the heat carrier, is used for
Coolant liquid is flow to coolant duct liquid outlet from coolant duct liquid inlet, is absorbed by coolant liquid and described thermally conductive proposes importing
Heat, wherein the coolant duct liquid outlet is connect with the gas-liquid heat exchanger；The gas-liquid heat exchanger, installation
In the bottom of the cargo tank structure body, for carrying out heat convection by coolant liquid and into the cold air of air passage, after cooling
Coolant liquid input liquid reserve tank；The air passage, including air inlet and air outlet lead to for entering cold air by air inlet
It crosses gas outlet hot-air is discharged.
Preferably, the covering setting of the prominent integrated bay section of the air inlet, the gas outlet and the integrated bay section
The conformal setting of covering.
Preferably, the gas-liquid heat exchanger gondola configuration it is external and with the conformal setting of covering.
Preferably, the payload module loading area is 8, installs 25 payload modules in each payload module loading area.
Preferably, the coolant duct is using going here and there and combining cooling liquid flowing channel topological structure, including 9 groups of cooling tubes, often
Group cooling tube includes 25 road cooling tubes, and 9 groups of cooling tubes are respectively arranged in 9 heat carriers, wherein 225 road cooling tubes are according to 3 groups
Series connection liquid inlet, 9 groups of liquid outlets arrangements, each group of liquid inlet flow through in 3 groups of strings and the cooling line of combination, every road cooling tube
Circulation path is equal, elbow number is identical, and coolant liquid is consistent with local resistance by the on-way resistance of every road cooling tube.
Preferably, the heat carrier is using high thermal conductivity mesophase pitch-based carbon fibers material as heat passage, wherein institute
Stating fibrous material is parallel arrangement, hot-forming Unidirectional Composites.
The embodiment of the present invention provides a kind of extraordinary unmanned plane, including above-mentioned extraordinary unmanned plane structure-function integration bay section.
Using the embodiment of the present invention, guarantee to set electronics under platform bearer mechanical characteristic and payload module environmental suitability
Standby structure incorporates in unmanned aerial vehicle platform structure, improves the multiplexing ratio of bearing structure, removes the weight of redundancy structure and components.
By payload module, High Density Integration installs and designs and layout type, improves arrangement space utilization rate, cable in platform cabin
With the maintainability of electric connector, multitask load mounting arrangement space anxiety is solved the problems, such as, realize platform integrated configuration.
The above description is only an overview of the technical scheme of the present invention, in order to better understand the technical means of the present invention,
And it can be implemented in accordance with the contents of the specification, and in order to allow above and other objects of the present invention, feature and advantage can
It is clearer and more comprehensible, the followings are specific embodiments of the present invention.
Detailed description of the invention
By reading the following detailed description of the preferred embodiment, various other advantages and benefits are common for this field
Technical staff will become clear.The drawings are only for the purpose of illustrating a preferred embodiment, and is not considered as to the present invention
Limitation.And throughout the drawings, the same reference numbers will be used to refer to the same parts.In the accompanying drawings:
Fig. 1 is the repacking schematic diagram of extraordinary unmanned plane in the prior art；
Fig. 2 is the integrated bay section appearance schematic diagram in the embodiment of the present invention based on unmanned platform；
Fig. 3 is the concrete structure schematic diagram of extraordinary the unmanned plane structure and function integration bay section of the embodiment of the present invention；
Fig. 4 is the structural schematic diagram of cargo tank structure body in the embodiment of the present invention；
Fig. 5 is the structural schematic diagram of liquid cooling cycle cooling system in the embodiment of the present invention；
Fig. 6 is the schematic diagram of series-parallel runner topological structure in the embodiment of the present invention.
Specific embodiment
In order to guarantee the flying quality and task execution time of extraordinary UAV system, structure lightened, mission payload with
Platform integrated configuration is to solve flying platform and task system to add one of contradictory measure of repacking, be guarantee system-wide performance with
The important channel that function operates normally.
The technical solution of the embodiment of the present invention designs a kind of suitable from modern integrated layout and light-weight design theory
It is more for below deck equipment, the structure and function integration bay section of the high extraordinary unmanned plane of power consumption.Guaranteeing platform structure bearing capacity
On the basis of learning performance and payload module installation environment adaptability, the structure of the avionics that need to be installed additional and task system electronic equipment is melted
Enter in the segment structure of unmanned engine room, improve the multiplexing ratio of bearing structure, removes redundancy structure and components.Meanwhile integrated bay section
Bearing structure integrally uses carbon fibre composite, and total system construction weight is greatly lowered, and realizes light-weight design.
By high-density installation modularization load design and reasonable decomposition layout type, space utilization in platform cabin is improved
The maintainability of rate, cable and electric connector.Meanwhile designing a kind of liquid cooling circulation cooling suitable for extraordinary unmanned plane below deck equipment
System, by by the coolant liquid topology runner of high power electronic equipment with heat pipe pattern and unmanned engine room segment structure integration realization knot
Structure and the design of thermal control function integration and layout, meanwhile, liquid-cooling circulating system liquid supply assembly integrates, and reduces interconnecting piece number of packages
Amount.Gas-liquid heat-exchange is conformal with section structure, reduces aerodynamic drag.
Exemplary embodiments of the present disclosure are described in more detail below with reference to accompanying drawings.Although showing the disclosure in attached drawing
Exemplary embodiment, it being understood, however, that may be realized in various forms the disclosure without should be by embodiments set forth here
It is limited.On the contrary, these embodiments are provided to facilitate a more thoroughly understanding of the present invention, and can be by the scope of the present disclosure
It is fully disclosed to those skilled in the art.
The structure and function integration bay section of the embodiment of the present invention are based on certain one segment structure of class unmanned aerial vehicle platform fuselage, dimension
It holds and designs on the basis of its existing aerodynamic configuration, as shown in Figure 2.Integrated bay section maximum outer profile outer dimension is 3400mm
× 1060mm × 1150mm (length × width × height).
Fig. 3 is the concrete structure schematic diagram of extraordinary the unmanned plane structure and function integration bay section of the embodiment of the present invention, such as
It is basic by cargo tank structure body, payload module, cable and connector, liquid cooling cycle cooling system, maintenance hatch door etc. shown in Fig. 3
Part forms.
Integrated bay section is divided into 8 payload module loading areas, is integrated with 200 VITA or ASAAC normal loading modules altogether.
25 payload modules are packed into each loading frame, top shield by 1 cover plate for sealing, bottom 30 cables of connection with connect
Device.Top, bottom and the two sides of cargo tank structure body are respectively arranged 5 fans maintenance hatch door, are used for payload module, wire and cable connector and liquid
The handling replacement of the apparatus assemblies such as SAPMAC method cooling system and daily maintenance.Liquid cooling cycle cooling system is by liquid supply assembly, gas-liquid
Heat exchanger and coolant duct composition, liquid supply assembly and gas-liquid heat-exchange are mounted on integrated cabin segment trailer side and (navigate with flight
To on the contrary), coolant duct is integrated in cargo tank structure body.
Primary structure is specifically described below.
1, cargo tank structure body
The integrated cabin segment structure body of the embodiment of the present invention is by the load structures such as traditional equipment frame, cabinet and unmanned plane
Platform structure carries out integrated design, improves bearing structure and is multiplexed ratio, removes redundancy structure and extra component weight.Cabin
Segment structure body integrally uses composite Materials Design, generally significantly reduces weight, saves space, maximizes and is laid out sky in cabin
Between, and be suitable for the highdensity payload module of task system and integrate, as shown in Figure 4.8 normal loading modules of cargo tank structure body point
Backboard is installed in loading area, each loading area inside front-back installation aluminium alloy base plate and heat conductor, bottom, and electromagnetism is installed at top
Shield gasket cover board.Each loading area inside configuration presetting preburied part and mounting hole keep pcb board, the insulation board of original machine case
Equal telecommunications functor reserves electric connector, the interfaces such as cable passage, so that payload module and external in bay section loading area bottom
Business electronic equipment interconnects.Generally, in the case where guaranteeing heat transfer and telecommunication functional conditions, tradition electronic equipment chassis is realized
With the integrated design of fuselage compartment section bearing structure, structure multiplexing ratio and space utilization rate are improved.
Reinforcing frame is devised between each loading area, has both born the mechanical property of transmitting, enhances structural strength, and tie up
Bay section exterior skin aerodynamic configuration is held.This reinforcing frame can be modified for the unmanned aerial vehicle platform structure of different aerodynamic configurations and set
Meter.
Integrated cabin segment structure body is both the main bearing capacity structure of unmanned aerial vehicle platform and the carrying of task system payload module
Structure.Cargo tank structure body main structure is manufactured for integration, and reinforcing frame assembling is spliced.Using T700 carbon/epoxy composite
Material panel and the former and the molecular composite sandwich structural of Nomex honeycomb core are in integrative design.Tables 1 and 2 is respectively
T700/603 carbon/epoxy composite material and the cellular performance parameter of Nomex.
1 carbon of table/epoxy composite material mechanical property parameters
Table 2Nomex-NRH-3-58 cellular material parameter
| Compressive strength/MPa | 1.85 |
| Compression modulus/MPa | 160.5 |
| L is to shear strength/MPa | 1.28 |
| L is to modulus of shearing/MPa | 53.4 |
| W is to shear strength/MPa | 0.63 |
| W is to modulus of shearing/MPa | 30.1 |
2, liquid cooling cycle cooling system integrated design
According to structure and function integration mentality of designing, integrated cabin segment structure body had both been the bearing structure of payload module,
The liquid-cooling heat radiation component of integrated load module again.It, can be pre- since integrated bay section main structure is honeycomb composite sandwich structure
Bury liquid cooling heat control system associated components, therefore, in each load zones of integrated cabin segment structure body, be embedded to reserved coolant liquid input and
The heat pipe pattern coolant flow channel and heat carrier of delivery outlet realize cargo tank structure body collection integrated with liquid cooling cycle cooling system
At.
Liquid cooling cycle cooling system is made of 5 components, i.e., pre-buried coolant duct, heat carrier, liquid supply assembly, gas-liquid heat
Exchanger and its air passage, as shown in Figure 5.Wherein, liquid supply assembly is by the devices such as pump, liquid reserve tank, control valve and filter one
Change and integrate, gives coolant liquid to provide driving force, overcome flow resistance.The integrated connecting tube reduced between attachment of liquid supply assembly
Road mitigates weight, improves Maintainability And Reliability.
The working principle of liquid cooling cycle cooling system of the present invention is each load zones load mould under the driving that liquid supply assembly pumps
The heat that block generates when working conducts in the coolant liquid flowed into pipeline liquid inlet through heat carrier, and flows through peace by pipeline liquid outlet
Plate-fin gas-liquid heat-exchange mounted in bay section bottom carries out heat convection with the cold air for entering air passage, and coolant liquid is through convection current
Enter liquid reserve tank body after cooling, in the ringing of pump, realizes the continual and steady heat dissipation of payload module.Heat carrier is set to two
Between the aluminium alloy base plate of payload module loading area and the head-tail of payload module loading area, for exporting the payload module work
As when the heat that generates into the coolant liquid of coolant duct.
The air passage of bay section bottom introduces extraneous punching press cold air by the air inlet outside protrusion bay section covering in Fig. 5, with
Hot-air is discharged for covering conformal gas outlet.Gas-liquid heat-exchange is whole can also be external with the conformal design of covering with gondola configuration,
The volume of cooling system is reduced, provides more installation spaces for cabin inner electronic equipment.
Fig. 6 is to go here and there and combine cooling liquid flowing channel topological structure.225 road cooling tubes according to 3 groups of series connection liquid inlets (a1~a3),
9 groups of liquid outlets arrange (b1~b9), and each group of liquid inlet flows through in 3 groups of strings and the cooling line of combination.It goes here and there and combines in Fig. 5 and set
The 1-25 cooling line of meter is according to arranged in series after No. 1-7, No. 8-13, No. 14-18,19-25 parallel connection.Every road cooling tube
Circulation path is equal, elbow number is essentially identical, on-way resistance and local resistance basic one of the coolant liquid by every road cooling tube
It causes.
Cargo tank structure body is carbon fibre composite in the embodiment of the present invention, is needed between payload module heat and tube-cooled liquid
The heat transfer of special designing realization rapidly and efficiently is wanted, i.e. the heat transfer of aluminium alloy base plate and heat carrier in Fig. 5 designs in Fig. 4.Mesh
Before, Fig. 5 heat carrier uses high thermal conductivity mesophase pitch-based carbon fibers material as heat passage, along the thermal conductivity of machine direction
Up to 1000W/mK, as shown in table 3.Fibers parallel is arranged, hot-forming Unidirectional Composites, along fiber side
To thermal conductivity can be up to 874Wm-1K-1, using machine direction transmit heat, the heat of payload module is quickly passed
It is directed in tube-cooled liquid, while it has stretching and shear strength, meets mechanics of materials requirement, as shown in table 4.
3 carbon fiber performance of table
4 composite property of table
In conclusion the key point of the embodiment of the present invention is as follows:
1, it on the basis of inheriting former unmanned aerial vehicle platform aerodynamic configuration, devises and is suitable for extraordinary unmanned plane structure and function one
Body bay section realizes platform and the modern integrated layout of electronic tasks system, lightweight and modularized design.
2, devising one kind is both the main bearing capacity structure of unmanned aerial vehicle platform and task system payload module bearing structure
Integrated cabin segment structure body is realized and incorporates the structure of electronic equipment in avionics and task system in platform structure.
3, the cargo tank structure loading area and its layout pattern for designing a kind of high-density installation payload module, improve nobody
Space utilization rate and modularization degree of integration, improve maintenance maintenance in platform cabin.
4, a kind of coolant duct and heat carrier integrated with cargo tank structure body is devised, and devises and is suitable for mark
The string and convolution runner topological structure of quasi- payload module realize structure and the design of thermal control function integration and are laid out.
5, the liquid cooling for devising a kind of extraordinary unmanned plane multi-load task system more suitable for below deck equipment, heat consumption is high is followed
Ring cooling system.
It is an advantage of the current invention that from modern integrated layout and structure and function integration design concept, design
A kind of unmanned aerial vehicle platform structure that, multitask load system that heat consumption high more suitable for below deck equipment installs additional and function integration cabin
Section.Guarantee under platform bearer mechanical characteristic and payload module environmental suitability, the structure of electronic equipment is incorporated into unmanned aerial vehicle platform
In structure, the multiplexing ratio of bearing structure is improved, removes the weight of redundancy structure and components.Pass through payload module, high density
Integrated installation design and layout type improve arrangement space utilization rate, the maintainability of cable and electric connector in platform cabin, solution
Certainly multitask load mounting arrangement space anxiety problem realizes platform integrated configuration.Meanwhile devising a kind of be suitable in cabin
The liquid cooling cycle cooling system for the extraordinary unmanned plane multi-load task system that equipment is more, heat consumption is high, and by high power electronic equipment
Series-parallel liquid-cooling heat radiation runner and unmanned engine room segment structure Integrated design, realize structure it is integrated with heat control system.Meanwhile
Liquid supply assembly integrates, and reduces connecting component quantity, and gas-liquid heat-exchange is conformal with section structure, reduces aerodynamic drag.One
Change bay section bearing structure and light-weight design is realized using carbon fibre composite, total system weight is greatly lowered, it is ensured that nothing
Under the premise of man-machine system flight characteristics, utmostly increases platform and take oil mass, improve task execution time.
The foregoing is only a preferred embodiment of the present invention, is not intended to restrict the invention, for the skill of this field
For art personnel, the invention may be variously modified and varied.All within the spirits and principles of the present invention, made any to repair
Change, equivalent replacement, improvement etc., should all be included in the protection scope of the present invention.
Claims (10)
1. a kind of special type unmanned plane structure-function integration bay section characterized by comprising
Cargo tank structure body for passing through payload module loading area installed load module, and is installed liquid cooling cycle cooling system, is passed through
The reinforcing frame being set between payload module loading area, enhancing structure intensity simultaneously maintain the pneumatic outer of integrated bay section exterior skin
Shape；
Payload module is installed in the payload module loading area of the cargo tank structure body, for undertaking mission payload；
Cable and connector are connect with the payload module, for realizing the payload module and external tasks electronic equipment
Connection；
Liquid cooling cycle cooling system, comprising: coolant duct, heat carrier, liquid supply assembly, gas-liquid heat exchanger and its air passage,
Wherein, liquid supply assembly, gas-liquid heat exchanger and its air passage are mounted on the integrated cabin segment trailer and the cargo tank structure body
And the side opposite with flight course, coolant duct and heat carrier are integrated in cargo tank structure body, for the bay section knot
Structure body radiates；
Safeguard that hatch door, including top maintenance hatch door, two sides maintenance hatch door and bottom safeguard hatch door, wherein the top maintenance
Hatch door is set to the top of cargo tank structure body, and the two sides maintenance hatch door is set to the two sides of the cargo tank structure body, the bottom
Portion's maintenance hatch door is set to the bottom of the cargo tank structure body, for facilitating payload module, cable and connector and liquid cooling to follow
The handling replacement of ring cooling system and daily maintenance.
2. integration bay section as described in claim 1, which is characterized in that the cargo tank structure body specifically includes: multiple load
Module loading area, each payload module loading area are separated by heat carrier, front-back installation inside each payload module loading area
Backboard is installed in aluminium alloy base plate, bottom, and top installation electromagnetic shielding seal cover board, the payload module loading area inside is for pacifying
Payload module is filled, and is provided with built-in fitting and mounting hole, keeps former lucky telecommunication functor；The payload module loading area
The interface of bottom pre- testing cable and connector；Reinforcing frame is provided between payload module loading area.
3. integration bay section as described in claim 1, which is characterized in that the cargo tank structure body is manufactured for integration,
Reinforcing frame assembling is spliced；The cargo tank structure body uses T700 carbon/epoxy composite material panel and T700 carbon/epoxy composite
Material panel and the molecular composite sandwich structural of Nomex honeycomb core.
4. integration bay section as described in claim 1, which is characterized in that the liquid cooling cycle cooling system specifically includes: cold
But liquid pipe road, heat carrier, liquid supply assembly, gas-liquid heat exchanger and its air passage, wherein the liquid supply assembly by pump, liquid reserve tank,
Control valve and filter is integrated forms, for giving coolant liquid to provide driving force, overcomes flow resistance, is input to cooling
Liquid pipe road liquid inlet；The heat carrier is set between the aluminium alloy base plate of two payload module loading areas and payload module loads
The head-tail in area, for exporting the heat generated when payload module work into the coolant liquid of coolant duct；It is described cold
But liquid pipe road is set in the heat carrier, is said for coolant liquid to be flow to coolant pipe from coolant duct liquid inlet
Liquid mouth absorbs the thermally conductive heat for proposing importing by coolant liquid, wherein the coolant duct liquid outlet and gas-liquid heat
Exchanger connection；The gas-liquid heat exchanger is installed on the bottom of the cargo tank structure body, is used for coolant liquid and enters ventilation
The cold air in road carries out heat convection, and coolant liquid after cooling is inputted liquid reserve tank；The air passage, including air inlet and outlet
Mouthful, for entering cold air by air inlet, hot-air is discharged by gas outlet.
5. integration bay section as claimed in claim 4, which is characterized in that the covering of the prominent integrated bay section of the air inlet is set
It sets, the conformal setting of covering of the gas outlet and the integrated bay section.
6. integration bay section as claimed in claim 4, which is characterized in that the gas-liquid heat exchanger gondola configuration it is external and with
The conformal setting of covering.
7. integration bay section as described in claim 1, which is characterized in that the payload module loading area is 8, each load
25 payload modules are installed in module loading area.
8. integration bay section as claimed in claim 7, which is characterized in that the coolant duct is using string and combines coolant liquid
Runner topological structure, including 9 groups of cooling tubes, every group of cooling tube includes 25 road cooling tubes, and 9 groups of cooling tubes are respectively arranged at 9 and lead
It is hot internal, wherein 225 road cooling tubes flow through 3 groups of strings according to 3 groups of series connection liquid inlets, 9 groups of liquid outlets arrangements, each group of liquid inlet
And in the cooling line combined, the circulation path of every road cooling tube is equal, elbow number is identical, and coolant liquid passes through every road cooling tube
On-way resistance it is consistent with local resistance.
9. integration bay section as described in claim 1, which is characterized in that the heat carrier uses high thermal conductivity intermediate phase pitch-based
Carbon fibre material is as heat passage, wherein the fibrous material is parallel arrangement, hot-forming Unidirectional Composites.
10. a kind of special type unmanned plane, which is characterized in that including extraordinary unmanned plane structure described in any one of claims 1 to 9
Function integration bay section.
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110525677A (en) * | 2019-08-21 | 2019-12-03 | 侯百文 | A kind of liquid cooling power transmission is electronic to be tethered at UAV system |
| CN111902033A (en) * | 2020-09-09 | 2020-11-06 | 南京工业职业技术大学 | Unmanned aerial vehicle with circuit board heat radiation structure |
| CN113220012A (en) * | 2021-04-06 | 2021-08-06 | 中国电子科技集团公司电子科学研究院 | Integrated cabin section for swarm unmanned aerial vehicle and swarm unmanned aerial vehicle |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2936219A1 (en) * | 2008-09-23 | 2010-03-26 | Airbus France | FUSELAGE STRUCTURE FOR COMBINED FASTENING OF INSULATION MATTRESSES AND EQUIPMENT, AIRCRAFT INCORPORATING SUCH A STRUCTURE. |
| CN103029845A (en) * | 2011-09-30 | 2013-04-10 | 空中客车运营简化股份公司 | Method of integrating avionics bay and floor structure for implementation |
| CN103402873A (en) * | 2011-02-22 | 2013-11-20 | 空中客车运营简化股份公司 | Heat exchanger built into a wall of an aircraft |
| CN107972843A (en) * | 2017-11-09 | 2018-05-01 | 中国运载火箭技术研究院 | A kind of lightweight, high maintainable unmanned plane composite structure system |
| CN207565824U (en) * | 2017-11-10 | 2018-07-03 | 江苏美龙航空部件有限公司 | A kind of unmanned plane forebody structure |
| CN209938923U (en) * | 2018-12-28 | 2020-01-14 | 中国电子科技集团公司电子科学研究院 | Special unmanned aerial vehicle structure function integration cabin section and special unmanned aerial vehicle |
-
2018
- 2018-12-28 CN CN201811618423.4A patent/CN109606612A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2936219A1 (en) * | 2008-09-23 | 2010-03-26 | Airbus France | FUSELAGE STRUCTURE FOR COMBINED FASTENING OF INSULATION MATTRESSES AND EQUIPMENT, AIRCRAFT INCORPORATING SUCH A STRUCTURE. |
| CN103402873A (en) * | 2011-02-22 | 2013-11-20 | 空中客车运营简化股份公司 | Heat exchanger built into a wall of an aircraft |
| CN103029845A (en) * | 2011-09-30 | 2013-04-10 | 空中客车运营简化股份公司 | Method of integrating avionics bay and floor structure for implementation |
| CN107972843A (en) * | 2017-11-09 | 2018-05-01 | 中国运载火箭技术研究院 | A kind of lightweight, high maintainable unmanned plane composite structure system |
| CN207565824U (en) * | 2017-11-10 | 2018-07-03 | 江苏美龙航空部件有限公司 | A kind of unmanned plane forebody structure |
| CN209938923U (en) * | 2018-12-28 | 2020-01-14 | 中国电子科技集团公司电子科学研究院 | Special unmanned aerial vehicle structure function integration cabin section and special unmanned aerial vehicle |
Non-Patent Citations (1)
| Title |
|---|
| 张利珍;王晓明;董素君;王浚;: "高超声速飞行器热载荷计算及影响因素分析", 北京航空航天大学学报, no. 03, 15 March 2009 (2009-03-15), pages 308 - 312 * |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110525677A (en) * | 2019-08-21 | 2019-12-03 | 侯百文 | A kind of liquid cooling power transmission is electronic to be tethered at UAV system |
| CN111902033A (en) * | 2020-09-09 | 2020-11-06 | 南京工业职业技术大学 | Unmanned aerial vehicle with circuit board heat radiation structure |
| CN113220012A (en) * | 2021-04-06 | 2021-08-06 | 中国电子科技集团公司电子科学研究院 | Integrated cabin section for swarm unmanned aerial vehicle and swarm unmanned aerial vehicle |
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